US11125318B2 - Power transmission system including a lubrication oil recovery device and turbomachine provided with such a power transmission system - Google Patents

Power transmission system including a lubrication oil recovery device and turbomachine provided with such a power transmission system Download PDF

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Publication number
US11125318B2
US11125318B2 US16/421,140 US201916421140A US11125318B2 US 11125318 B2 US11125318 B2 US 11125318B2 US 201916421140 A US201916421140 A US 201916421140A US 11125318 B2 US11125318 B2 US 11125318B2
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oil
transmission system
power transmission
annular
recovery chamber
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US20190360578A1 (en
Inventor
Fabrice Joel Luc CHEVILLOT
Julien Fabien Patrick Becoulet
Arnaud Nicolas NEGRI
Emmanuel Pierre Dimitri Patsouris
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Assigned to SAFRAN AIRCRAFT ENGINES reassignment SAFRAN AIRCRAFT ENGINES ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BECOULET, JULIEN FABIEN PATRICK, CHEVILLOT, FABRICE JOEL LUC, NEGRI, ARNAUD NICOLAS, PATSOURIS, EMMANUEL PIERRE DIMITRI
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/04—Features relating to lubrication or cooling or heating
    • F16H57/042—Guidance of lubricant
    • F16H57/0427—Guidance of lubricant on rotary parts, e.g. using baffles for collecting lubricant by centrifugal force
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/06—Arrangements of bearings; Lubricating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H1/00—Toothed gearings for conveying rotary motion
    • F16H1/28—Toothed gearings for conveying rotary motion with gears having orbital motion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/04—Features relating to lubrication or cooling or heating
    • F16H57/042—Guidance of lubricant
    • F16H57/0421—Guidance of lubricant on or within the casing, e.g. shields or baffles for collecting lubricant, tubes, pipes, grooves, channels or the like
    • F16H57/0423—Lubricant guiding means mounted or supported on the casing, e.g. shields or baffles for collecting lubricant, tubes or pipes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/04—Features relating to lubrication or cooling or heating
    • F16H57/0456—Lubrication by injection; Injection nozzles or tubes therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/04—Features relating to lubrication or cooling or heating
    • F16H57/0467—Elements of gearings to be lubricated, cooled or heated
    • F16H57/0479—Gears or bearings on planet carriers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/04—Features relating to lubrication or cooling or heating
    • F16H57/048—Type of gearings to be lubricated, cooled or heated
    • F16H57/0482—Gearings with gears having orbital motion
    • F16H57/0486—Gearings with gears having orbital motion with fixed gear ratio
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/324—Application in turbines in gas turbines to drive unshrouded, low solidity propeller
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/325—Application in turbines in gas turbines to drive unshrouded, high solidity propeller
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/609—Deoiling or demisting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/98—Lubrication
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the field of the present invention is that of aeronautical propulsion and more particularly that of turbomachines with rotating parts requiring significant lubrication.
  • Some turbomachines such as dual flow turbine engine or turboprop engine with counter-rotating propellers, are equipped with a power transmission mechanism such as epicyclic gear train differential speed reducer or a planetary gear train speed reducer (known as a “RGB” or “Reduction Gear Box”).
  • a power transmission mechanism such as epicyclic gear train differential speed reducer or a planetary gear train speed reducer (known as a “RGB” or “Reduction Gear Box”).
  • Epicyclic gear train differential speed reducers i.e. wherein all components are movable, are applicable to turboprop engines with twin propellers.
  • Planetary gear reducers i.e. wherein the planet carrier is fixed and the ring gear is movable, are applicable to a turboprop engine with a single propeller or a dual flow turbine engine equipped with a fan. Examples of power transmission mechanisms are described in US-A1-2017/254407 and FR-A1-3054264.
  • a power transmission shaft drives the fan shaft of the dual flow turbine engine or the rotor shaft of the propellers via the speed reducer.
  • Fan shafts or propeller shafts are supported and guided by bearings that include rolling elements such as balls or rollers.
  • Such speed reducers are equipped with several rotating gear wheels and/or pinions whose lubrication is an essential aspect for the proper functioning of the turbomachine and its efficiency.
  • friction between the teeth of the gear wheels and/or pinions or at the bearings causes premature wear and thus a decrease in the speed reducer's efficiency.
  • the lubrication system consists of one or more housings forming an enclosure in which the speed reducer and bearings are contained.
  • the oil is generally evacuated to the lower part of the enclosure (six o'clock).
  • the enclosure also includes evacuation means such as pipes that return oil back into the lubrication system.
  • evacuation means are arranged, in a complex manner, in the lower part of the outer ring gear so as to evacuate the oil from the internal parts of the speed reducer towards the lower part of the enclosure.
  • evacuation is more complex.
  • Patent No. FR3052322 describes an example of an epicyclic gear train differential speed reducer and an oil recovery device that prevents oil from accumulating in the enclosure by forming accumulation zones and quickly evacuating the oil.
  • the recovery device includes an annular gutter arranged around the outer ring gear of the speed reducer.
  • the gutter includes a recovery chamber and a first portion of wall arranged at least partially facing oil ejection means in order to guide the oil projected onto it towards the oil recovery chamber.
  • the first wall portion is a fin that forms an orifice oriented towards the ejection means. This fin is surrounded by other portions of annular walls forming a bowl and the chamber has a lateral inlet opening through which the oil passes.
  • this gutter is its radial size, which affects the mass of the turbomachine.
  • this gutter is complex because of its many walls, fins and bowls shaped to avoid oil retention and the guiding of the oil to the recovery chamber, which influences the manufacturing cost and feasibility of the recovery device and the turbomachine.
  • the objective of this invention is in particular to provide an improved recovery system that quickly recovers, contains and evacuates a large oil flow to a lubrication system while being simple in design and reducing the radial size of the gutter.
  • the position of the recovery chamber makes it possible not to impact the radial size in an enclosure already cluttered with the speed reducer and bearings because the chamber does not extend beyond this outlet port of the speed reducer.
  • the configuration of the gutter is easy to manufacture and implement while allowing, on the one hand, the relative displacements between the outer ring gear of the speed reducer and the gutter and, on the other hand, efficient oil recovery. Indeed, since the outer ring gear is movable, most of the oil is evacuated from the outer ring gear via the annular tab and by means of centrifugal force with great force.
  • the recovery chamber is therefore as close as possible to the periphery of the outer ring gear of the speed reducer, in particular the annular tab, to reduce the radial size.
  • the outer diameter of the system is reduced while avoiding radial clearance between moving and fixed parts of the system.
  • the speed reducer is a differential reducer or a planetary reducer.
  • the planet carrier is fixed in relation to the sun gear.
  • the annular tab includes an annular periphery and the orthogonal projection of the annular periphery being arranged radially outside the recovery chamber.
  • the gutter includes a second wall portion connected at one of its ends to the first wall portion and at another of its end to the recovery chamber, the inlet opening being arranged facing a part of the second wall portion.
  • the recovery chamber is arranged upstream of the annular tab of the outer ring gear, the first wall portion being connected to a third wall portion extending downstream of the annular tab.
  • the recovery chamber has a substantially U-shaped axial section in order to store a large quantity of oil and to prevent the oil from spilling into the turbomachine enclosure and in particular into the speed reducer installed in this enclosure with the gutter.
  • the gutter includes an annular retention wall secured to one of the side walls forming a branch of the U of the recovery chamber and bordering at least a portion of the inlet opening.
  • a retention wall improves the retention of the recovery chamber and prevents the oil from overflowing from the recovery chamber.
  • the first wall portion is conical or frustoconical so as to facilitate the guidance of the oil to the recovery chamber and prevent the oil from being directed towards the reducer.
  • the first wall portion is arranged axially opposite the recovery chamber so as to facilitate the progression of the oil to the recovery chamber.
  • the gutter is provided with a radial axis outlet opening located in the lowest part of the speed reducer along the radial axis and oriented towards the outside of the speed reducer so as to allow the oil to drain from the gutter to the lower part of the enclosure.
  • the gutter is made from a sheet metal. This makes it possible to have a light and economical gutter.
  • the recovery chamber is provided with a radially oriented inlet opening facing the gutter wall.
  • the gutter includes two axially opposed recovery chambers arranged on either side of the oil ejection means.
  • the oil ejection means have an angular orientation with respect to the radial axis, the orientation including an axial component along the longitudinal axis X towards the gutter.
  • Such a configuration can prevent splashes on the gutter wall when the oil is ejected by centrifugation.
  • the outer ring gear is fixed on the rotor shaft by means of a flange which includes at least partly the oil ejection means through which the oil is ejected by centrifugal effect.
  • the flange is formed by an annular support secured with the rotor shaft and extending radially outwardly, and an annular tab of the outer ring gear which extends radially outwardly, the annular tab and the annular support being supported against each other, the ejection means including channels formed between the annular support and the annular tab.
  • the rotor shaft is a fan shaft.
  • the outer ring gear is monobloc.
  • the outer ring gear is formed in two portions with a first ring portion and a second ring portion
  • the flange is formed in three portions with a first annular tab portion extending radially outwardly and integral with the first ring portion, a second annular tab portion extending radially outwardly and integral with the second ring portion, and an annular support extending radially outwardly and integral with a rotor shaft
  • the oil ejection means including channels formed at least between the support, the first and second annular tab portions.
  • the invention also concerns a turbomachine including a rotor shaft with a longitudinal axis X, a power shaft and a power transmission system having any of the above-mentioned characteristics, between the rotor shaft and the power shaft, the oil recovery device being arranged to recover and contain the oil ejected by centrifugal effect from the speed reducer.
  • FIG. 1 shows an axial and partial section of a turbomachine including a fan module whose fan shaft is driven by a power shaft via a speed reducer installed in a lubrication enclosure;
  • FIG. 2 is a schematic, axial and partial view of a gutter of a lubricant recovery device ejected from an outer ring gear of a planetary gear speed reducer according to the invention
  • FIG. 3 shows the lower part of the gutter of the recovery device shown in FIG. 2 ;
  • FIG. 4 shows a variant of FIG. 2 with a gutter with a curved or bent wall portion
  • FIG. 5 schematically illustrates another variant of the gutter according to the previous figure in which a retention wall prevents the lubricant from overflowing from a gutter recovery chamber;
  • FIG. 6 shows the lower part of a gutter according to another variant of FIG. 2 with a wall that widens towards a recovery chamber;
  • FIG. 7 shows another embodiment in which a recovery chamber is arranged upstream of the gutter and a radially outer flange of the outer ring gear of the speed reducer;
  • FIG. 8 illustrates another embodiment of the invention with a gutter of a lubricant recovery device comprising two recovery chambers
  • FIG. 10 is an axial and partial cross-sectional view of a part of a speed reducer comprising ejection means with several channels for ejecting oil at the periphery of a flange of the speed reducer.
  • the dual flow turbine engine 1 generally includes an external nacelle (not shown) enclosing a gas generator 2 upstream of which is mounted a fan 3 .
  • upstream and downstream are defined in relation to the gas flow in the turbomachine which is substantially parallel to the longitudinal axis X.
  • radial”, “internal”, “external”, “outer”, “outward”, “lower”, “upper”, “below” and “above” are defined with respect to a radial axis Z perpendicular to the longitudinal axis X and with respect to the distance from the longitudinal axis X.
  • the gas generator 2 includes, for example, from upstream to downstream, a low-pressure compressor 4 , a high-pressure compressor, a combustion chamber, a high-pressure turbine and a low-pressure turbine.
  • the high-pressure compressor is connected to the high-pressure turbine via a high-pressure shaft to form a high-pressure body.
  • the low-pressure compressor 4 is connected to the low-pressure turbine via a low-pressure shaft 5 to form a low-pressure body.
  • the low-pressure shaft 5 and the high-pressure shaft are centered on the longitudinal axis X.
  • the fan 3 is here enclosed by a fan housing (not shown) attached to the external nacelle.
  • the fan 3 compresses the air entering the turbomachine which is divided into a primary flow flowing through a primary annular duct 6 which passes through the gas generator 2 and a secondary flow flowing through a secondary 7 annular duct around the gas generator 2 .
  • the primary 6 and the secondary duct 7 are separated by an inter-duct 8 annular housing surrounding the gas generator 2 .
  • the fan 3 consists of a series of blades 11 , each extending radially outward and radially bounded by the fan housing.
  • the power transmission mechanism includes a speed reducer 12 , formed with a gear train known as a “Reduction Gear Box” (RGB).
  • the speed reducer is here planetary. This includes, as shown schematically in FIG. 1 , an inner sun gear referred to here as sun gear 15 , planet gears 16 , a planet carrier 17 and an outer sun gear referred to here as outer ring gear 18 .
  • the input of the speed reducer 12 is coupled to the low pressure shaft 5 while the output of the speed reducer 12 is coupled to the fan shaft 10 .
  • the speed reducer 12 includes an input shaft 19 , centered on the longitudinal axis X, rotationally fixed to the low-pressure shaft 5 and to the sun gear 15 along the longitudinal axis X.
  • the outer ring gear 18 also centered on the longitudinal axis X, is fixed in rotation with the fan shaft 10 about the longitudinal axis X.
  • Planet gears 16 for example, five in number, are carried by the planet carrier 17 , which is fixedly mounted.
  • the planet gears 16 each rotate about an axis substantially parallel to the longitudinal axis X.
  • Each of the planet gears 16 in the form of a pinion, has teeth that mesh with those of the sun gear 15 , in the form of a gear wheel, and with the outer ring gear 18 equipped with internal teeth.
  • the speed reducer can be an epicyclic gear train differential speed reducer.
  • the sun gear, planet gears, planet carrier and outer ring gear are all movable.
  • a third bearing 23 is also provided to support and guide the low-pressure shaft 5 in rotation.
  • This third bearing 23 is located downstream of the speed reducer 12 .
  • the third bearing 23 also includes an inner ring carried by the low-pressure shaft 5 and an outer ring carried by a downstream support 24 .
  • the first, second and third bearings 20 , 21 , 23 , as well as the gear wheels and pinions of the speed reducer 12 are contained in an annular lubrication enclosure 25 formed by one or more fixed housing(s) 26 of the turbomachine.
  • the ferrule 22 and the downstream support 24 are fixed to the fixed annular housing 26 .
  • This fixed housing 26 being itself fixed to the internal housing 9 of the turbomachine.
  • the enclosure 25 extends axially and radially on either side of the speed reducer 12 . As shown in FIG. 1 , this enclosure 25 is at least partially axially traversed by the fan shaft 10 and the low-pressure shaft 5 .
  • a lubrication system (not shown) includes pipes that spray oil through the sun gear 15 .
  • the oil is injected into the rotating parts of the planet gears 16 and sun gear 15 and then the outer ring gear 18 .
  • the oil is then ejected outside the outer ring gear 18 by centrifugation using ejection means 30 shown in more detail in FIG. 2 and following.
  • the oil is also injected at the first, second and third levels 20 , 21 , 23 .
  • FIG. 2 shows an example of fixing between the fan shaft 10 and the outer ring gear 18 of the speed reducer 12 in the upper part of the latter (high point, at 12 o'clock).
  • the ring gear 18 is monoblock (i.e. in one piece).
  • the outer ring gear 18 includes an annular tab 27 extending radially outwardly. This includes at least part of the ejection means as described below.
  • This annular tab 27 is fixed to an annular support 28 of the fan shaft 10 via fixing means 29 such as screws.
  • the annular support 28 extends along the radial axis Z to a free end of the fan shaft 10 .
  • This support 28 is defined in a plane parallel or substantially parallel to the one in which the annular tab 27 is defined.
  • the annular tab 27 and the support 28 form a flange 35 .
  • the oil is ejected from the outer ring gear 18 at this flange 35 via oil ejection means 30 .
  • Ejection means 30 here comprise one or more channels 31 which are evenly distributed at least over the circumference of the outer ring gear 18 .
  • the first channels 31 a extend substantially along the radial axis Z.
  • Each first channel 31 a extends radially between an inlet port 32 a and an outlet port 33 .
  • the inlet port 32 a is defined in an inner surface 34 of the outer ring gear 18 on which the inner teeth (not shown) are defined.
  • the outlet orifice 33 it leads to the periphery of the flange 35 (annular periphery 36 of the annular tab 27 and that of the support 28 which are flush).
  • outlet ports 33 there are several outlet ports 33 distributed circumferentially over the periphery of the flange 35 , and at least three outlet ports 33 are provided on the periphery of the flange 35 .
  • the oil flows from the inside of the outer ring gear 18 to the outside of it via channel(s) 31 .
  • second channels 31 b extend substantially along the longitudinal axis X.
  • Each second channel 31 b extends axially from an inlet port 32 b and a first channel 31 a .
  • the second channels 31 b lead to the first channels 31 a.
  • the lubricating oil is expelled through channels 31 with a radial speed corresponding to the centrifugation exerted by the passage through the outer ring gear 18 and a tangential speed corresponding to the rotational drive at the third speed in the direction of rotation of the outer ring gear 18 .
  • the power transmission system is completed by an oil recovery device 40 which is designed to quickly recover and evacuate the oil ejected by centrifugal effect into the turbomachine and in particular into the enclosure 25 .
  • This recovery device 40 includes an annular gutter 41 designed to recover the oil ejected from the speed reducer 12 .
  • the gutter 41 centered on the longitudinal axis X, is arranged around the outer ring gear 18 .
  • the gutter 41 is fixed on the fixed housing 26 .
  • the gutter 41 includes a recovery chamber 42 through which a large quantity of oil passes before it is evacuated to the lower part of the enclosure 25 .
  • the size of the recovery chamber allows the oil to be temporarily accumulated or stored in order to limit overflows.
  • the gutter 41 also includes a first wall portion 43 arranged at least partially facing the oil ejection means 30 , here channels 31 , 31 a , 31 b and configured so as to direct the oil projected by centrifugation onto it towards the recovery chamber 42 .
  • recovery chamber 42 is located downstream of gutter 41 , and here downstream of flange 35 .
  • the recovery chamber 42 is open.
  • the chamber is oriented substantially radially outwardly.
  • the recovery chamber 42 has a substantially U-shaped axial section with a bottom 44 , an inlet opening 45 radially opposite the bottom 44 , first and second side walls 46 a , 46 b (with respect to the longitudinal axis X).
  • the side walls 46 a , 46 b each form a branch of the U.
  • the inlet opening 45 is oriented radially outwardly.
  • the first wall portion 43 is located facing the flange 35 .
  • the wall 43 is located radially at a distance from the ring gear (and the annular tab, or even the flange 35 ).
  • This one is connected to a second wall portion 47 which is connected to one of the side walls 46 a , 46 b of the recovery chamber 42 (here the first side wall 46 a ).
  • the second wall portion 47 extends substantially along the longitudinal axis X with a part facing the ejection means and the outer ring gear 18 .
  • the inlet opening 45 is arranged facing the gutter wall 41 (and in particular part of the second wall portion 47 ).
  • the bottom 44 of recovery chamber 42 is oriented towards the outer ring gear 18 .
  • the connection between the second wall portion 47 and the first side wall 46 a is here approximately at a right angle.
  • the first wall portion 43 has a conical or frustoconical axial section so that the oil is diverted to the recovery chamber 42 , in this example downstream of gutter 41 .
  • the first wall portion 43 conical or frustoconical is arranged axially opposite the recovery chamber 42 .
  • the oil projected on the first wall portion 43 progresses along the second wall portion 47 towards the inlet opening 45 of recovery chamber 42 .
  • a free end 48 of the first wall portion 43 is oriented towards the inside of the turbomachine (towards the speed reducer 12 ).
  • the free end 48 is located upstream of flange 35 and in particular upstream of the annular support 28 of fan shaft 10 .
  • the oil cannot therefore be sprayed beyond the free end 48 , towards the enclosure 25 .
  • the gutter 41 includes a third wall portion 49 that is attached to the fixed housing 26 by fastening devices 50 such as bolts or screws.
  • the third wall portion 49 is coupled to one of the side walls 46 a , 46 b of the recovery chamber.
  • the third wall portion 49 is attached to the second side wall 46 b adjacent to the annular tab 27 of the outer ring gear 18 .
  • the third wall portion 49 has a first radial portion 49 a which is attached to the second side wall 46 b and a second portion 49 b which extends radially below the bottom 44 of the recovery chamber 42 .
  • an annular collar 49 c with a radial axis Z is fixed on the fixed housing 26 .
  • the inlet opening 45 is defined in the same plane or in a substantially lower plane in which the outlet port 33 of the ejection means is defined, here channels 31 and outlet ports 33 .
  • Recovery chamber 42 does not extend beyond outlet port 33 of the channels.
  • the RC radius of recovery chamber 42 is equal to or less than the external radial height (radius RP) of annular tab 27 or flange 35 .
  • the radius RP is defined as the distance between the longitudinal axis X and the annular periphery 36 of the annular tab 27 or the flange 35 while the radius RC of the recovery chamber 42 is considered as the distance between the longitudinal axis X and the inlet opening 25 .
  • the recovery chamber 42 has a height along the radial axis that is substantially equal to or lower than that of annular tab 27 .
  • the orthogonal projection of the annular periphery 36 (of the annular tab 27 ) on the side wall 46 a of the recovery chamber 42 forms a line at point 36 P that is arranged radially outside the recovery chamber.
  • the flange 35 is located radially inside the gutter 41 .
  • the gutter 41 is also equipped with an outlet port 37 with a radial axis oriented towards the inside of the turbomachine.
  • the recovery chamber can include several outlet ports 37 .
  • Each outlet port 37 is formed in the second wall portion 47 of the gutter.
  • the outlet port 37 is located at least partially with respect to recovery chamber 42 .
  • the oil is evacuated from the lower part of the gutter 41 (i.e. outside the speed reducer) and toward the lower part of the enclosure 25 at six o'clock to return to the lubrication circuit of the lubrication system.
  • the gutter 41 is made of a metallic material. In an advantageous way, but not limited to, the gutter 41 is made from a sheet metal to lighten the weight of the latter.
  • the walls 43 , 44 , 47 , 46 a , 46 b , 49 are obtained by bending or welding. Bending and welding are easy and quick to implement and require very little tooling to manufacture the gutter.
  • FIG. 4 illustrates a variant of the embodiment described above.
  • the gutter 41 of this variant is substantially identical to the one described in FIGS. 2 and 3 except for the configuration of the second wall portion 47 of the gutter.
  • the second wall portion 47 has a conical or frustoconical axial section. Its upstream end, integral with the first wall portion 43 , is oriented towards the inside of the turbomachine. In other words, the second wall portion 47 widens downstream.
  • the second wall portion 47 includes an angled portion 52 that connects to the first side wall 46 a of recovery chamber 42 to optimize oil flow toward the recovery chamber 42 .
  • FIG. 5 also shows another embodiment of the gutter 41 , according to the invention.
  • the second wall portion 47 has a conical or frustoconical axial section and the bent or elbowed portion 52 downstream of the gutter 41 as described in FIG. 4 .
  • the gutter 41 includes an annular retention wall 51 that is attached to the second side wall 46 b of the recovery chamber 42 to improve its retention.
  • the retention wall 51 borders the inlet opening 45 of recovery chamber 42 .
  • the retention wall 51 has an inclination with respect to the radial axis Z. This is particularly oriented towards the upstream side of the gutter, i.e. towards the first wall portion 43 of the gutter 41 .
  • This retention wall is formed by bending or attaching and then welded to the second side wall 46 b .
  • the oil is sprayed from channels 31 to gutter 41 and then into the recovery chamber 42 of the latter following the same path described in relation to FIG. 4 .
  • FIG. 7 illustrates another embodiment in which the recovery chamber 42 is located upstream of the gutter 41 . More precisely, the recovery chamber 42 is located upstream of the annular support 28 of the fan shaft 10 and upstream of the oil ejection means 30 including the channels 31 .
  • the first wall portion 43 axially opposite the recovery chamber 42 , is arranged facing the oil ejection means 30 and surrounds the oil ejection means.
  • the third wall portion 49 attached to the fixed housing 26 , is connected to the first wall portion 43 conical or frustoconical. This third wall portion 49 extends downstream of the annular tab 27 of the outer ring gear 18 .
  • the gutter 41 includes two axially opposed recovery chambers 42 a , 42 b arranged on either side of the oil ejection means 30 . These recovery chambers 42 a , 42 b each have smaller dimensions than the previous embodiments, which also reduces the radial size.
  • the gutter 41 includes two first portions 43 a , 43 b of conical or frustoconical wall facing the oil ejection means 30 . These form a V whose apex is oriented towards the ejection means 30 .
  • Each of the first wall portions 43 a , 43 b guides the oil to a recovery chamber 42 a , 42 b .
  • each first wall portion 43 a , 43 b widens respectively towards the corresponding recovery chamber 42 a , 42 b in which the oil is diverted.
  • Each first wall portion 43 a , 43 b is connected to a side wall of the recovery chamber via a second wall portion 47 a , 47 b .
  • the second wall portions 47 a , 47 b extend along the longitudinal axis but these can of course widens towards a recovery chamber (conical or frustoconical section) as shown in FIGS. 4 and 5 .
  • the side wall 46 a can connect the second wall portion 47 b with a bent portion 52 or with a right angle.
  • the oil When the oil is sprayed onto the first wall portion 43 a (downstream of flange 35 on FIG. 8 ), the oil is directed towards the recovery chamber 42 a (downstream of the flange 35 ) along the second wall 47 a .
  • the oil sprayed on the first wall portion 43 b is directed to the recovery chamber 42 b (upstream of the flange 35 ) in the same way.
  • FIG. 9 illustrates a variant of the gutters described in relation to FIGS. 2 to 8 .
  • the ejection means 30 have at least one portion with an angular orientation with respect to the radial axis Z.
  • each ejection channel 31 a of ejection means 30 has a portion that is inclined at an angle of about 45° with the radial axis Z and is oriented towards the second wall portion 47 .
  • each channel 31 a is oriented (towards the outer radial end of the channel 31 a ) towards the recovery chamber 42 depending on whether the latter is upstream or downstream of the ejection means 30 or flange 35 to avoid oil splashes in the gutter and enclosure 25 .
  • the oil is sprayed directly onto the second wall 47 (arrow F 3 ) and then progresses along it until it reaches the recovery chamber (arrow F 4 ).
  • the first wall portion 43 also allows any oil splashes to be directed towards the recovery chamber 42 .
  • the outer ring gear 18 ′ is formed in two portions. This means that it is no longer monoblock as shown in FIGS. 2 to 9 .
  • the annular tab carried by the outer ring gear 18 ′ is also made in two portions.
  • the flange 35 ′ is made up of three portions (support and two-part annular tab).
  • the outer ring gear 18 ′ includes a first ring portion 18 a which is provided with a first annular tab portion 27 a . The latter extends radially outwardly.
  • the ring gear includes a second ring portion 18 b which is equipped with a second annular tab portion 27 b .
  • First channels 310 a are formed between the radial face of the support 28 and a first radial wall 38 a of the first annular tab portion 27 a . Each first channel 310 a is connected to a second channel 310 b formed on the circumference of the first ring portion 18 a.
  • First channels 310 a ′ are also formed between a second radial wall 38 b of the first annular tab portion 27 a and the radial surface of the second annular tab portion 27 b .
  • the first and second radial walls 38 a , 38 b are axially opposed to each other.
  • Each first channel 310 a ′ is connected to a second channel 310 b ′ formed on the circumference of the first ring portion 18 b (especially on the circumference of the projection 53 ). In this way, the oil passes through the speed reducer 12 and is ejected by centrifugal effect from the outer ring gear 18 ′ by penetrating through the inlet port or ports 32 a ′ according to arrow F 1 .
  • the oil surrounding the speed reducer also progresses on the periphery of the outer ring gear 18 ′ by centrifugal effect to enter the inlet 32 b ′ port according to arrow F 10 .
  • the oil then progresses through the second channels 310 b , 310 b ′, then through the first channels 310 a , 310 a ′ which are formed between the walls of the fan shaft 10 and the first and second annular tab portions 27 a , 27 b of the outer ring gear 18 ′ according to arrows F 11 , F 11 ′, F 2 , F 2 ′ until it is projected onto the gutter 41 then into a recovery chamber 42 or into two recovery chambers 42 a , 42 b.
  • the radial and possibly axial sizes in the turbomachine are reduced, in particular with an outer ring gear 18 , 18 ′ rotating in relation to a fixed housing, so as not to impact the mass of the latter.
  • the recovery chamber 42 , 42 a , 42 b allows a total recovery of the centrifuged oil through the outer ring gear 18 , 18 ′ of the speed reducer 12 .
US16/421,140 2018-05-28 2019-05-23 Power transmission system including a lubrication oil recovery device and turbomachine provided with such a power transmission system Active 2040-04-22 US11125318B2 (en)

Applications Claiming Priority (2)

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FR1854532A FR3081513B1 (fr) 2018-05-28 2018-05-28 Systeme de transmission de puissance comprenant un dispositif de recuperation d'huile de lubrification et turbomachine equipee d'un tel systeme de transmission de puissance
FR1854532 2018-05-28

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US11125318B2 true US11125318B2 (en) 2021-09-21

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US (1) US11125318B2 (fr)
EP (1) EP3575562B1 (fr)
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US20230184167A1 (en) * 2020-05-13 2023-06-15 Safran Aircraft Engines Aircraft turbomachine comprising a device for lubricating a bearing

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FR3086341B1 (fr) * 2018-09-24 2020-11-27 Safran Aircraft Engines Turbomachine a reducteur pour un aeronef
FR3096275B1 (fr) * 2019-05-24 2021-06-18 Safran Helicopter Engines Pièce pour dégazeur centrifuge de turbomachine avec parois longitudinales adaptées
FR3107089B1 (fr) * 2020-02-07 2023-03-10 Safran Aircraft Engines Retenue axiale d’une soufflante dans un turboréacteur
US11365688B2 (en) 2020-08-04 2022-06-21 G.E. Avio S.r.l. Gearbox efficiency rating for turbomachine engines
US11401829B2 (en) 2020-08-04 2022-08-02 Ge Avio S.R.L. Gearbox efficiency rating for turbomachine engines
US11473507B2 (en) 2020-08-04 2022-10-18 Ge Avio S.R.L. Gearbox efficiency rating for turbomachine engines
US11486312B2 (en) 2020-08-04 2022-11-01 Ge Avio S.R.L. Gearbox efficiency rating for turbomachine engines
FR3117171B1 (fr) 2020-12-03 2022-10-21 Safran Systeme de transmission de puissance comportant une gouttiere de recuperation d’huile amelioree
FR3123700A1 (fr) 2021-06-07 2022-12-09 Safran Transmission Systems Piece mecanique pour une turbomachine d’aeronef et turbomachine correspondante.
IT202100015386A1 (it) 2021-06-11 2022-12-11 Ge Avio Srl Turbomacchine e gruppi ad ingranaggi epicicloidali con canali di lubrificazione
IT202100018032A1 (it) * 2021-07-08 2023-01-08 Ge Avio Srl Turbina a gas
IT202100029891A1 (it) 2021-11-25 2023-05-25 Ge Avio Srl Impianto di lubrificazione integrato
FR3130892B1 (fr) 2021-12-17 2023-12-15 Safran Trans Systems Dispositif de récupération de lubrifiant dans une turbomachine
IT202200001613A1 (it) 2022-01-31 2023-07-31 Gen Electric Valutazione di efficienza motoristica complessiva per motori a turbomacchina
FR3136014A1 (fr) 2022-05-24 2023-12-01 Safran Transmission Systems Gouttiere de canalisation d’huile pour une turbomachine
FR3137720A1 (fr) * 2022-07-07 2024-01-12 Safran Aircraft Engines Dispositif de recuperation d’huile pour une turbomachine
FR3138472A1 (fr) 2022-08-01 2024-02-02 Safran Transmission Systems Gouttière de récupération d’huile pour un réducteur de turbomachine

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FR3081513B1 (fr) 2021-06-18
US20190360578A1 (en) 2019-11-28
CN110541760A (zh) 2019-12-06
EP3575562A1 (fr) 2019-12-04
FR3081513A1 (fr) 2019-11-29
EP3575562B1 (fr) 2021-06-30

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